• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.35-35
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• 2000

추력 편향제어(Thrust Vector Control)는 위성 발사체나 대륙간 탄도 미사일과 같이 공기가 희박한 고 고도에서의 비행자세 제어와 궤도수정, 지대공이나 함대공 유도탄처럼 발사 직후 저속에서 임의의 방향으로 급선회해야 할 경우에 노즐의 배출가스 방향을 직접 조절하여 모멘트를 발생시키는 제어방식을 말한다. 이 방식 중 널리 사용되고 있는 제트 베인 추력 편향제어방식은 베인이 직접 고온, 고속의 가스 흐름내에서 작용하기 때문에 재료는 내열성과 제트 베인 주위에 형성되는 유동 특성, 그리고 베인간의 유동 간섭이 중요한 인자이다. 그러므로, 제트 베인의 실용화는 수치해석에 의존하던 개발 초기나 중기의 설계 단계에서 벗어나 실제 크기나 축소모델의 유동 모사 시험에 의해 성능이 검증되어야 한다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.227-230
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• 2008

Movable nozzle with a flexible seal have been used for Thrust Vector Control of the Solid Rocket Motor. The Hydraulic Testing Machine is consisted of Chamber, Actuator, Counterpotentiometer, and evaluates performance of Flexible seal for spring torque and axial compression. The qualification test of Flexible seal was conducted on design condition. A study fix up method of formulation, operation, inspection on Hydraulic testing machine.

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.162-170
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• 2005

In KSLV-I, actuation system for thrust vector control of kick motor was configured as electro-hydraulic servo actuation system and consisted of actuators, hydraulic power supply system, hydraulic power distribution system and control system. In case of hydraulic power supply system, we use EMDP(Electric Motor Driven Pump) to supply hydraulic power. Generally, we use brushed DC motor for EMDP but it is not easy to operate EMDP using brushed DC motor at a high altitude. Hence, we are developing EMDP using brushless DC motor to use at a high altitude. In this study, we will explain control system for BLDC motor to drive hydraulic pump.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.88-94
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• 2004

The KSR-III rocket is a liquid propellant sounding rocket and thrust vector control actuators and cold gas thrusters are used to control pitch and yaw, roll attitude respectively during thrusting phase. In this paper, the structure of designed attitude controller and gain scheduling, results of stability analysis for KSR-III rocket are presented. The attitude controller is implemented with flight software in the domestically developed INS and successfully performed its function in the flight test. The flight data are coincident with simulation results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.6
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• pp.116-123
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• 2002

This paper describes the development of gimbals engine actuation system for KSR(Korean Sounding Rocket)-III which performs the attitude control of pitch and yaw axes by thrust vector control of liquid propellant gimbals engine. The development requirements of configuration, performance and environment are introduced, and the principles and details of components and system development are discussed. The developed system successfully fulfilled its own performance and environmental evaluation. It will be planned to perform verification of interface and integration compatibility with other related systems, and then mounted on KSR-III as a flight hardware system.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.15 no.5
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• pp.1207-1212
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• 2011

This paper presents a study on the DSP(Digital Signal Processor) controller for the PBW(power-by-wire) system using BLDC(Brushless Direct Current) servo motor pump. The PBW hydraulic actuator was realized with hydraulic pump driven by BLDC servo motor, hydraulic cylinder and controller. This PBW system needs speed control of servo motor for linear thrust action of hydraulic cylinder. This paper implements a servo controller with vector control algorithm and MIN-MAX PWM technique. As CPU of a controller, TMS320F2812 DSP was adopted because it has PWM waveform generator, A/D converter, SPI(Serial Peripheral Interface) port and many input/output port etc.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.213-220
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• 2010

This paper presents the analysis results of trajectory, performance and attitude control based on the first flight data of the KSLV-I. The KSLV-I had a fairing separation problem and failed to inject spacecraft into the orbit. In this paper, the trajectory, flight performance, and attitude control was analyzed considering the influence of unseparated fairing. Moreover, the flight results and performance of the inertial navigation and guidance system were presented. As a results of post-flight analysis, any other problem besides the fairing separation problem was not happened and onboard equipment functioned normally.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.110-116
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• 2008

This paper gives a brief summary of the TVC battery design description, specifications and test results. The TVC battery for KSLV-I upper stage contains 168 Sony l8650VT high power lithium-ion cells. It configured as 2 strings in parallel, with each string containing 84 series connected cells. This allows to meet nominal 270V voltage and capacity requirements specified for the mission of the Thrust Vector Control(TVC) system. The loads profile of the TVC system has short duration, high current pulse. To power such a system with minimal mass, the battery employed l8650VT Cells. This cell is specifically designed for high rate applications and is capable of a 10C continuous discharge.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.41-44
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• 2006

The propulsion system of VIA-50A airship consists of engine, generator, inverter, motor and propeller. The motor and propeller was designed that can be tilted to $120^{\circ}$ for thrust vector control. When the flight test was performed, various condition data of the airship were obtained by wireless telecommunication and analyzed in real-time. In this paper, we presented flight test results of propulsion system. Considering the designed requirement and normal range, we verified that all constituent part was operated in normal condition during the high altitude flight test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.34-34
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• 1998

차세대 비행체가 갖추어야 할 요건으로 다양한 작동 범위에서 다목적으로 사용될 수 있어야 한다는 점이다. 비행체는 작전시 초음속으로 순항해야 하며, 폭탄으로 손상된 비행장에서도 이륙하여 작동할 수 있도록 짧은 이륙과 착륙 거리를 가져야 하기 때문에 현재 비행체보다 더 큰 받음각에서 작동하여 비행시 뛰어난 기동성을 가져야 한다. 제어력을 향상시키기 위해서 받음각과 동압에 의존하지 않고 큰 제어 모멘트를 제공하는 차세대 방법은 엔진의 배기가스를 원하는 비행 방향으로 제어하는 것으로 이러한 방법을 추력 편향 제어(Thrust Vector Control)라고 한다. 기존 공력에 의한 비행 자세제어 방법은 속도의 2승에 비례하는 제어력을 발생하지만, 실속을 피해야하기 때문에 공기력을 이용한 날개 및 비행체의 받음각에 한계가 있어 비행체의 선회능력을 제한하며 고공에서 저속비행 하는 경우에는 공기의 밀도가 낮고 동압이 작게 작용하여 선회능력은 낮아진다. 그러나, 추력 편향 장치는 공력을 이용하지 않고 추력을 이용하기 때문에 실속에 의한 제한이 없어 큰 받음각(70$^{\circ}$-90$^{\circ}$)으로 선회할 수 있어 월등한 기동성을 발휘할 수 있다. 이러한 추력 편향 장치 중 제트 베인형은 소형화가 가능하고, 하나의 노즐로 수직, 수형 및 횡 방향의 3축 제어를 할 수 있어 많이 사용되고 있다.